US6685431B2 - Method for repairing a turbine vane - Google Patents

Method for repairing a turbine vane Download PDF

Info

Publication number
US6685431B2
US6685431B2 US10/002,419 US241901A US6685431B2 US 6685431 B2 US6685431 B2 US 6685431B2 US 241901 A US241901 A US 241901A US 6685431 B2 US6685431 B2 US 6685431B2
Authority
US
United States
Prior art keywords
platform
replacement
vane
machined
detail
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime, expires
Application number
US10/002,419
Other languages
English (en)
Other versions
US20030077171A1 (en
Inventor
David J. Hiskes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HISKES, DAVID J.
Priority to US10/002,419 priority Critical patent/US6685431B2/en
Priority to GB0221936A priority patent/GB2381224B/en
Priority to SG200205914-5A priority patent/SG131751A1/en
Priority to FR0212350A priority patent/FR2832338B1/fr
Priority to DE10249392A priority patent/DE10249392B4/de
Priority to JP2002309850A priority patent/JP3839389B2/ja
Publication of US20030077171A1 publication Critical patent/US20030077171A1/en
Publication of US6685431B2 publication Critical patent/US6685431B2/en
Application granted granted Critical
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Adjusted expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to a method for repairing a vane used in a gas turbine engine.
  • Re-airfoiling replaces the airfoil section of a turbine vane with a new cast airfoil, while re-using the original platforms.
  • This type of repair has been used on first stage turbine vanes in commercial jet engines. In this type of repair, the airfoil is joined to the platforms by butt welded joints within the airfoil.
  • a full vane repair is performed on first stage vanes.
  • the airfoil and the outer platform are entirely replaced by using a single butt weld in the airfoil.
  • vane nozzle area is maintained by a re-strike of the airfoil after all joining has been completed. There remains a need for a more effective repair vane repair technique.
  • a method for repairing a vane used in a gas turbine engine broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress, and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement detail having at least a replacement first platform, a replacement first buttress, and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion and the replacement detail.
  • FIG. 1 is a perspective view of a vane to be repaired.
  • FIG. 2 is a perspective view of the vane of FIG. 1 with the inner platform, the inner buttress, the airfoil, and part of the outer platform and the outer buttress removed.
  • FIG. 3 is a perspective view of a replacement detail used in the method of the present invention.
  • FIG. 4 is a perspective view of a vane repaired in accordance with the present invention.
  • the vane 10 has an inner platform 11 , an inner buttress 12 , an outer platform 13 , an outer buttress 14 , and an airfoil 16 extending between the inner platform 11 and the outer platform 13 .
  • the outer buttress 14 has a plurality of bolt holes 18 for joining the vane 10 to another engine component.
  • FIG. 2 illustrates the portion 15 of the vane 10 remaining after the vane 10 has been machined to remove the inner platform 11 , the inner buttress 12 , and the airfoil 16 in their entirety and a central portion of the outer platform 13 and a portion of the outer buttress 14 .
  • the aforementioned parts of the vane 10 may be removed using any suitable technique known in the art such as grinding, milling, or wire EDM.
  • a notch 22 is formed in the rear buttress flange 23 of the outer buttress 14 as a result of the removal step.
  • the notch 22 preferably extends above the surface 24 of the buttress trailing edge extension.
  • a central portion 28 of the outer platform 13 between the rear buttress flange 23 and the forward buttress flange 30 has been removed leaving platform side rails 32 and 34 .
  • the cuts used to remove the central portion 28 are made so that when the replacement detail 40 shown in FIG. 3 is inserted between the platform side rails 32 and 34 , the airfoil portion 42 of the replacement detail 40 is properly staggered in the repaired vane 10 ′ and the proper flow area is provided between the replacement airfoil 42 and the airfoils of adjacent vanes.
  • Nozzle area is controlled by the angle at which the surfaces 36 and 38 of the platform side rails 32 and 34 are cut and the angle of the mating surfaces on the replacement detail 40 . This enables the entire replacement airfoil 42 to be rotated to adjust the nozzle area.
  • FIG. 3 illustrates a replacement detail 40 which is used to repair the vane 10 .
  • the replacement detail 40 has an integrally formed replacement inner platform 43 , a replacement inner buttress 44 , and the replacement airfoil 42 .
  • the replacement detail 40 also has an integrally formed new central portion 46 to be seated between platform side rails 32 and 34 , which central portion includes a replacement outer platform portion 45 , an integrally formed raised portion 48 to be positioned in the notch 22 , which raised portion 48 extends above the surface of the central portion 46 , and an integrally formed replacement buttress trailing edge extension 50 .
  • the replacement detail 40 may be a cast structure having the aforementioned features.
  • the replacement detail may be formed from the same material forming the vane 10 or a compatible material.
  • FIG. 4 illustrates a repaired vane 10 ′ after the replacement detail 40 has been positioned relative to the machined vane portion 15 and joined thereto.
  • the replacement detail 40 and the machined vane portion 15 may be joined together using any suitable welding or brazing technique known in the art. It is preferred to use a diffusion brazing technique to join the replacement detail 40 and the machined vane portion 15 .
  • the diffusion brazing is carried out by applying a brazing material, such as a boron-containing cobalt-base brazing alloy, to the surfaces of the replacement detail 40 and the machined vane portion 15 to be joined together. After application of the brazing material, the machined vane portion 15 and the replacement detail 40 are placed in a furnace.
  • the repaired vane 10 ′ is then heated to a first temperature in the range of 2190° F. to 2240° F. for a time period in the range of from 1 minute to 20 minutes at a pressure in the range of 0.0005 Torr or lower. Thereafter, the repaired vane 10 ′ is heated to a second temperature in the range of 2125° F. to 2175° F. for a time period in the range of from 1 minute to 10 minutes at an atmospheric pressure of 0.0005 Torr or lower. Thereafter, the repaired vane is cooled to a third temperature in the range of from about 2085° F. to about 2115° F., preferably at a rate of approximately 1° F./minute. The repaired vane is then held at the third temperature for a time period in the range of 8 to 12 hours. After completion of this initial cooling down period, the repaired vane 10 ′ is allow to cool down to room temperature (approximately 68° F.).
  • the repair method of the present invention results in a repaired vane that has no welds in the airfoil.
  • the strength of material in the joint is less than the base alloy.
  • the airfoil is exposed to the highest temperature and high strength in the airfoil providing a more durable vane. Further, since the joint is subject to lower temperatures than the airfoil, the requirements on the joint are lower.
  • the repair method of the present invention allows control of the vane nozzle area by machining of the joint surfaces instead of by an additional re-strike operation.
  • Re-strike of the vane changes the airfoil camber to correct the nozzle area.
  • Re-strike can be expected to induce microcracking in the areas that are deformed, particularly at the trailing edge root and tip.
  • Re-strike also changes the airfoil shape from the optimal. For these reasons, re-strike is undesirable.
  • nozzle area is controlled in the inventive method by the angle at which the joint surface is produced on the machined vane portion and the replacement detail. The entire airfoil is rotated to adjust area.
  • Airfoil cooling usually relies on maintaining a closely controlled fit between the internal baffle and inner vane wall. Mismatch at weld joints in the airfoil reduce the cooling effectiveness.
  • the repair method of the present invention is sufficiently effective to allow a conventional internal baffle to vane fit as good as on a new vane.
  • the two dimensional joint configuration used in the method of the present invention allows simple machining by grinding, milling, or wire EDM.
  • the fit at the joint can be controlled to the tolerances required for using a brazing process such as diffusion brazing.
  • the method of the present invention requires less platform machining while maintaining original outer platform ground surfaces, seal slots, and bolt holes.
  • any inner platform machining can be done using outer platform machined surfaces as datums.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/002,419 2001-10-24 2001-10-24 Method for repairing a turbine vane Expired - Lifetime US6685431B2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US10/002,419 US6685431B2 (en) 2001-10-24 2001-10-24 Method for repairing a turbine vane
GB0221936A GB2381224B (en) 2001-10-24 2002-09-20 Method for repairing a turbine vane
SG200205914-5A SG131751A1 (en) 2001-10-24 2002-09-27 Method for repairing a turbine vane
FR0212350A FR2832338B1 (fr) 2001-10-24 2002-10-04 Procede pour reparer une aube de turbine, element de remplacement pour la mise en oeuvre du procede et aube ainsi reparee
DE10249392A DE10249392B4 (de) 2001-10-24 2002-10-23 Verfahren zum Reparieren einer Turbinenschaufel, sowie Austauschelement zur Verwendung bei der Reparatur
JP2002309850A JP3839389B2 (ja) 2001-10-24 2002-10-24 ベーンの修理方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/002,419 US6685431B2 (en) 2001-10-24 2001-10-24 Method for repairing a turbine vane

Publications (2)

Publication Number Publication Date
US20030077171A1 US20030077171A1 (en) 2003-04-24
US6685431B2 true US6685431B2 (en) 2004-02-03

Family

ID=21700659

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/002,419 Expired - Lifetime US6685431B2 (en) 2001-10-24 2001-10-24 Method for repairing a turbine vane

Country Status (6)

Country Link
US (1) US6685431B2 (ja)
JP (1) JP3839389B2 (ja)
DE (1) DE10249392B4 (ja)
FR (1) FR2832338B1 (ja)
GB (1) GB2381224B (ja)
SG (1) SG131751A1 (ja)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060104810A1 (en) * 2004-11-16 2006-05-18 Hagle Michael P Method for making a repaired turbine engine stationary vane assembly and repaired assembly
US20070084050A1 (en) * 2005-10-13 2007-04-19 Siemens Power Generation, Inc. Turbine vane airfoil reconfiguration method
US20070183692A1 (en) * 2006-02-08 2007-08-09 Pawloski James C Reclosable pouch and zipper for a reclosable pouch
WO2007081924A3 (en) * 2006-01-09 2008-01-17 Surface Technology Holdings Method of improving the properties of a repaired component and a component improved thereby
US20080179381A1 (en) * 2007-01-25 2008-07-31 United Technologies Corporation Diffusion braze repair of single crystal alloys
US20080213092A1 (en) * 2007-03-01 2008-09-04 Honeywell International, Inc. Repaired vane assemblies and methods of repairing vane assemblies
US20080265005A1 (en) * 2007-04-30 2008-10-30 United Technologies Corporation Brazing process incorporating graphitic preforms
US20080289179A1 (en) * 2007-05-22 2008-11-27 United Technologies Corporation Split vane repair
US20090000102A1 (en) * 2007-06-28 2009-01-01 Siemens Power Generation, Inc. Turbine vane restoration system
US20090068446A1 (en) * 2007-04-30 2009-03-12 United Technologies Corporation Layered structures with integral brazing materials
US20090067987A1 (en) * 2007-08-06 2009-03-12 United Technologies Corporation Airfoil replacement repair
US20090179064A1 (en) * 2008-01-10 2009-07-16 Turbine Overhaul Service Pte Ltd System and method for restoring metal components
US20090224027A1 (en) * 2008-03-10 2009-09-10 Turbine Overhaul Services Pte Ltd Method for diffusion bonding metallic components with nanoparticle foil
US20090274562A1 (en) * 2008-05-02 2009-11-05 United Technologies Corporation Coated turbine-stage nozzle segments
US20100061846A1 (en) * 2008-09-05 2010-03-11 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US20100196147A1 (en) * 2009-01-30 2010-08-05 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
US8763403B2 (en) 2010-11-19 2014-07-01 United Technologies Corporation Method for use with annular gas turbine engine component
US20150361807A1 (en) * 2013-03-07 2015-12-17 United Technologies Corporation Structural guide vane for gas turbine engine
US9271340B2 (en) 2007-10-26 2016-02-23 Turbine Overhaul Services Pte Ltd Microwave filter and microwave brazing system thereof
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102107306B (zh) * 2009-12-23 2013-06-05 沈阳黎明航空发动机(集团)有限责任公司 一种涡轮导向叶片缺陷的修补方法
EP3105447A4 (en) * 2014-02-05 2017-12-13 United Technologies Corporation Disposable fan platform fairing
US10436047B2 (en) 2015-08-18 2019-10-08 General Electric Company Method for repair of a diaphragm of a rotary machine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2071777A (en) 1980-03-19 1981-09-23 Gen Electric Method and replacement member for repairing a gas turbine engine vane assembly
US6195864B1 (en) * 1997-04-08 2001-03-06 Allison Engine Company, Inc. Cobalt-base composition and method for diffusion braze repair of superalloy articles
US6416278B1 (en) * 2000-11-16 2002-07-09 General Electric Company Turbine nozzle segment and method of repairing same

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3909157A (en) * 1972-01-27 1975-09-30 Chromalloy American Corp Turbine nozzle-vane construction
CA989153A (en) * 1972-08-22 1976-05-18 John M. Aartman Guide vane repair
US5269057A (en) * 1991-12-24 1993-12-14 Freedom Forge Corporation Method of making replacement airfoil components
DE19547903C1 (de) * 1995-12-21 1997-03-20 Mtu Muenchen Gmbh Verfahren zur Herstellung oder Instandsetzung von Schaufeln für Turbomaschinen mittels Laserstrahlauftragsschweißen unter Verwendung eines Metallpulvers als Zusatzwerkstoff, sowie Stützform zur Herstellung oder Instandsetzung derartiger Schaufeln und Verfahren zur Herstellung der Stützform
US5758416A (en) * 1996-12-05 1998-06-02 General Electric Company Method for repairing a turbine engine vane segment
DE19831736C2 (de) * 1998-07-15 2000-05-31 Mtu Muenchen Gmbh Verfahren zur Reparatur und Herstellung eines integral beschaufelten Rotors für eine Strömungsmaschine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2071777A (en) 1980-03-19 1981-09-23 Gen Electric Method and replacement member for repairing a gas turbine engine vane assembly
US6195864B1 (en) * 1997-04-08 2001-03-06 Allison Engine Company, Inc. Cobalt-base composition and method for diffusion braze repair of superalloy articles
US6416278B1 (en) * 2000-11-16 2002-07-09 General Electric Company Turbine nozzle segment and method of repairing same

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7172389B2 (en) * 2004-11-16 2007-02-06 General Electric Company Method for making a repaired turbine engine stationary vane assembly and repaired assembly
US20060104810A1 (en) * 2004-11-16 2006-05-18 Hagle Michael P Method for making a repaired turbine engine stationary vane assembly and repaired assembly
US7536783B2 (en) 2005-10-13 2009-05-26 Siemens Energy, Inc. Turbine vane airfoil reconfiguration method
US20070084050A1 (en) * 2005-10-13 2007-04-19 Siemens Power Generation, Inc. Turbine vane airfoil reconfiguration method
WO2007081924A3 (en) * 2006-01-09 2008-01-17 Surface Technology Holdings Method of improving the properties of a repaired component and a component improved thereby
US20070183692A1 (en) * 2006-02-08 2007-08-09 Pawloski James C Reclosable pouch and zipper for a reclosable pouch
US20080179381A1 (en) * 2007-01-25 2008-07-31 United Technologies Corporation Diffusion braze repair of single crystal alloys
US20080213092A1 (en) * 2007-03-01 2008-09-04 Honeywell International, Inc. Repaired vane assemblies and methods of repairing vane assemblies
US7959409B2 (en) * 2007-03-01 2011-06-14 Honeywell International Inc. Repaired vane assemblies and methods of repairing vane assemblies
US20080265005A1 (en) * 2007-04-30 2008-10-30 United Technologies Corporation Brazing process incorporating graphitic preforms
US8413877B2 (en) 2007-04-30 2013-04-09 United Technologies Corporation Layered structures with integral brazing materials
US20090068446A1 (en) * 2007-04-30 2009-03-12 United Technologies Corporation Layered structures with integral brazing materials
US8220150B2 (en) 2007-05-22 2012-07-17 United Technologies Corporation Split vane cluster repair method
US20080289179A1 (en) * 2007-05-22 2008-11-27 United Technologies Corporation Split vane repair
US8186056B2 (en) 2007-06-28 2012-05-29 Siemens Energy, Inc. Turbine vane restoration system
US20090000102A1 (en) * 2007-06-28 2009-01-01 Siemens Power Generation, Inc. Turbine vane restoration system
US7798773B2 (en) 2007-08-06 2010-09-21 United Technologies Corporation Airfoil replacement repair
US20090067987A1 (en) * 2007-08-06 2009-03-12 United Technologies Corporation Airfoil replacement repair
US9271340B2 (en) 2007-10-26 2016-02-23 Turbine Overhaul Services Pte Ltd Microwave filter and microwave brazing system thereof
US20090179064A1 (en) * 2008-01-10 2009-07-16 Turbine Overhaul Service Pte Ltd System and method for restoring metal components
US20090224027A1 (en) * 2008-03-10 2009-09-10 Turbine Overhaul Services Pte Ltd Method for diffusion bonding metallic components with nanoparticle foil
US7874472B2 (en) 2008-03-10 2011-01-25 United Technologies Corporation Method for diffusion bonding metallic components with nanoparticle foil
US20090274562A1 (en) * 2008-05-02 2009-11-05 United Technologies Corporation Coated turbine-stage nozzle segments
US8083465B2 (en) 2008-09-05 2011-12-27 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US20100061846A1 (en) * 2008-09-05 2010-03-11 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US8162603B2 (en) * 2009-01-30 2012-04-24 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
US20100196147A1 (en) * 2009-01-30 2010-08-05 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
US8763403B2 (en) 2010-11-19 2014-07-01 United Technologies Corporation Method for use with annular gas turbine engine component
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
US20150361807A1 (en) * 2013-03-07 2015-12-17 United Technologies Corporation Structural guide vane for gas turbine engine
WO2014138147A3 (en) * 2013-03-07 2016-01-07 United Technologies Corporation Structural guide vane for gas turbine engine
US9963984B2 (en) * 2013-03-07 2018-05-08 United Technologies Corporation Structural guide vane for gas turbine engine

Also Published As

Publication number Publication date
GB2381224A (en) 2003-04-30
DE10249392B4 (de) 2007-06-14
US20030077171A1 (en) 2003-04-24
DE10249392A1 (de) 2003-05-15
GB2381224B (en) 2003-12-17
FR2832338A1 (fr) 2003-05-23
JP2003161111A (ja) 2003-06-06
SG131751A1 (en) 2007-05-28
JP3839389B2 (ja) 2006-11-01
GB0221936D0 (en) 2002-10-30
FR2832338B1 (fr) 2006-09-08

Similar Documents

Publication Publication Date Title
US6685431B2 (en) Method for repairing a turbine vane
US7966707B2 (en) Method for repairing superalloy components using inserts
US6173491B1 (en) Method for replacing a turbine vane airfoil
JP4375930B2 (ja) タービンエンジン羽根の台板のレーザークラッディング
EP1759799B1 (en) Method for forming or remanufacturing a turbine engine component
US6413650B1 (en) Method for repairing superalloy castings using a metallurgically bonded tapered plug
US8220150B2 (en) Split vane cluster repair method
JPS641641B2 (ja)
JPS64562B2 (ja)
EP1605068A2 (en) Homogeneous welding via pre-heating for high strength superalloy joining and material deposition
EP1419849A1 (en) Fabricated repair of cast nozzle
US20130004320A1 (en) Method of rotated airfoils
US20090113706A1 (en) Craze crack repair of combustor liners
US20090028707A1 (en) Apparatus and method for repairing airfoil tips

Legal Events

Date Code Title Description
AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HISKES, DAVID J.;REEL/FRAME:012352/0145

Effective date: 20011024

STCF Information on status: patent grant

Free format text: PATENTED CASE

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

FPAY Fee payment

Year of fee payment: 4

FPAY Fee payment

Year of fee payment: 8

FPAY Fee payment

Year of fee payment: 12

AS Assignment

Owner name: RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS

Free format text: CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001

Effective date: 20200403

AS Assignment

Owner name: RAYTHEON TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:055659/0001

Effective date: 20200403